Rocket launcher for launching rockets with high initial acceleration



United States Patent [56] References Cited UNITED STATES PATENTS1,347,125 7/1920 Schneider.......

[72] Inventors John R. Munger Huntsville;

, Sherman E. Tate, l-lartselle, Ala. ['21] Appl.No. 733,193

et al 2,867,153 1/1959 Hirsch............ 3,071,073 1/1963Ammann........ 3,134,330 5/1964 Batou.......

3,282,161 11/1966 MacDonald, Jr

[22] Filed May 29, 1968 {45] Patented Dec. 29, 1970 [73] Assignee TheUnited States of America as represented by the Secretary of the ArmyPrimary Examiner-Samuel W. Engle Attorneysl-1arry M. Sarag ovitz, EdwardJ. Kelly, Herbert Earl and J. Keith Fowler ROCKET LAUNCHER FOR LAUNCHINGROCKETS WITH HIGH INITIAL ACCELERATION DEDICATORY CLAUSE The inventiondescribed herein may be manufactured, used, and licensed by or for theGovernment for governmental purposes without the payment to us of anyroyalty thereon.

BACKGROUND OF THE INVENTION The present invention relates to rocketlaunchers and recoil type guns wherein a reverse gun action is effected.

Prior art mechanisms of this type rely primarily on closed breech boostor gun boost. While these mechanisms are efficient, they require a veryheavy, bulky barrel or tube. These are more difficult to transport andare inherently more expensive than is desired.

SUMMARY OF THE INVENTION An improved rocket launcher, which functions ona reversegun" concept, is provided. Thus, high initial acceleration iseffected due to the pressure created between the solid propellant andthe face of the mandrel, this pressure being applied prior to theeffective propelling force created at the rocket nozzle and, thus, beingcomplementary thereto.

BRIEF DESCRIPTION OF THE DRAWING FIG. 1 is an axial cross-sectionalview, with portions broken away, of a loaded rocket launcher accordingto the present invention; and

FIG. 2 is a view similar to that of FIG. 1, but showing a modified formof the invention.

DESCRIPTION OF THE PREFERRED EMBODIMENTS In the drawing, FIG. 1,reference numeral 1 indicates generally a rocket launcher according tothe present invention including a launch tube or firing tube 2 supportedwithin a tubular housing 4 carried by launcher support member 6. Supportmember 6 is pivotally secured at 8 to the launcher base I and issupported in elevation at its other end at I2 by the upper end of thebipod mount 14. Rocket 20, shown in the loaded position within thelaunch tube, includes a cylindrical motor casing 22, a nose section 24on the fore end of the casing, and an exhaust nozzle 25 on the aft endof the casing. A removable end plate 26 closes the aftend of the nozzleand is provided with an axial bore 28. A solid propellant grain 30 isdisposed within the motor casing in a conventional manner. The grain isformed with a burning surface defined by an axial bore 32 extending fromits aft end to a predetermined point short of the fore end thereof. Amandrel 36 is removably secured as at 38 to the launcher base andextends coaxially through end plate bore 28 and coaxially within grainbore 32. The mandrel may be of any design which permits rigid attachmentto the launcher base. In addition, the mandrel used in casting the motorgrain may be left therein and utilized. For igniting the propellant, anigniter 40 is placed at the fore end of the mandrel. While the igniteris shown in its preferred location secured to the fore end of themandrel, the same may also be supported within the space 42 between thefore end of mandrel and the end of the grain bore; or the igniter may besecured to the propellant grain at the end of the grain bore. Theigniter may be activated electrically by external means (not shown)connected thereto as by conductors 43.

Referring now to FIG. 2, wherein a modified form of the invention isillustrated, mandrel 50 is arranged for telescoping action. Thus,tubular mandrel 50 is formed with a piston 52 on its fore end forsliding engagement within outer cylinder 56.

Spring-loaded balls or detent means 54 provided in the peripheral wallof the piston are adapted for interlocking engagement within the annularmating groove 58 provided in the inner wall of cylinder 56.

OPERATION OF THE PREFERRED EMBODIMENTS OF THE INVENTION In theembodiment of FIG. I when the igniter is activated, the propellant willburn initially in a substantially closed system thereby producing a highpressure for forcing the missile away from the mandrel. Hence, thefiring of the device according to this invention is similar to a gunboost wherein the pressure volume work of the gases imparts energy tothe rocket at a rate comparable to that of a projectile in a gun untilthe rocket has traveled the length of that portion of the mandrel whichextends within the rocket motor grain. When the aft end of thepropellant grain passes the upper end of the mandrel, i.e., when themandrel has been withdrawn from the grain bore, the rocket motoroperates with its nozzle in conventional fashion.

The operation of the embodiment of FIG. 2 is similar to that of FIG. 1with the sole difference being in the telescoping action of the mandrel.Thus, upon activation of the igniter means, as pressure builds up inchamber 42, the missile moves toward the fore end of the launch tubecarrying cylinder 56 therewith. Thus, the telescoping mandrel moves fromits collapsed condition (as depicted in FIG. 2) to an extended conditionwherein the detent balls 54 are engaged matingly within groove 58.Increased pressure in the chamber 42 then causes the missile to movecoaxially along the outer cylinder 56 until the same has traveled theentire length of the cylinder. Accordingly, this arrangement providesfor a longer time period during which the missile grain engages themandrel, the telescoping arrangement operating to extend the effectivelength of the mandrel.

Since certain changes may be made in the structure described withoutdeparting from the scope of the invention, it is intended that allmatter contained in the above description, or shown in the accompanyingdrawings, shall be interpreted as generally illustrative and not in astrictly limiting sense.

We claim:

I. In a rocket launcher for launching a rocket, said rocket beingdefined by a motor having an exhaust nozzle on its aft end, a bodyportion, and a nose portion; a solid propellant grain disposed withinsaid body portion, said propellant grain being formed with an axial boreopening into the motor exhaust nozzle and extending forwardly apredetermined distance short of the forward end of the grain, an endclosure removably secured on the aft end of the motor exhaust nozzle,said end closure having a central aperture formed therein, said launchercomprising: a rigid mount; a firing tube secured at its aft end to saidmount; support structure secured to said tube adjacent the fore endthereof for maintaining the tube in elevated disposition; a telescopingmandrel removably secured at its aft end to said mount and extendingthrough the aperture in the end closure, said mandrel extending into thegrain bore a predetermined distance short of the fore end of said boreso as to define a space between the end of said mandrel and the end ofsaid bore; said mandrel including an inner cylindrical member and anouter cylindrical member, said inner cylindrical member having a pistonon its fore end, detent means carried by said piston, said outercylindrical member having an annular groove within its aft end, saiddetent means being adapted for interlocking engagement in said groovewhen said mandrel is in an extended condition; and igniter meansdisposed within said space for igniting said propellant.

